CN103850716B - The part span shroud of tear drop shape - Google Patents
The part span shroud of tear drop shape Download PDFInfo
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- CN103850716B CN103850716B CN201310627609.7A CN201310627609A CN103850716B CN 103850716 B CN103850716 B CN 103850716B CN 201310627609 A CN201310627609 A CN 201310627609A CN 103850716 B CN103850716 B CN 103850716B
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- 239000000567 combustion gas Substances 0.000 claims description 12
- 238000010276 construction Methods 0.000 description 10
- 238000002485 combustion reaction Methods 0.000 description 6
- 238000013016 damping Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/74—Shape given by a set or table of xyz-coordinates
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention discloses a kind of part span shroud of the tear drop shape of the rotating vane in turbine, and the rotatable blades include：Airfoil section, the airfoil section has leading edge, trailing edge, radially-inwardly holds and radially outward hold；Root segment, the root segment is connected on the radially-inwardly end of the airfoil section.Part span shroud（part‑span shroud）It is positioned on the airfoil section, between the root segment and the radially outward end.The part span shroud is substantially tear drop shape, and to cause such as to be measured from the leading edge of the part span shroud, the maximum gauge of its shape of cross section is located within 20% to 40% of the chord length of extension between the leading edge and trailing edge of the part span shroud.
Description
Technical field
The present invention generally relates to the rotating vane in turbine.More particularly, the present invention relates in adjacent leaf
Rotating vane with part span shroud between piece.
Background technology
Fluid flow path such as steam or the turbine of combustion gas turbine is generally formed by fixed shell and rotor.
In this construction, multiple fixed blades are attached on housing in the way of circumferential array, and extend radially inwardly to flow path
In.Similarly, multiple rotating vanes are attached on rotor in the way of circumferential array and extend radially outwardly into flow path
In.Fixed blade and rotating vane are arranged to alternate row, to cause that the blade of a skate leaf and direct downstream row forms one
" level ".The grade wheel blade is used for guiding flow path, with so that the flow path is entered in the blade of downstream row with correct angle.
The aerofoil profile of blade extracts energy from working fluid, thus produce drive rotor and be attached to thereon load necessary to move
Power.
The blade of turbine they rotate at high speed when, can suffer from vibration and axial torsion.Asked to solve these
Topic, blade is typically included in the portion being placed on airfoil section at the intermediate radial distance between the tip of each blade and root segment
Divide span shroud.The grade part span shroud is typically connected to the pressure of each aerofoil profile（It is convex）Face and suction（It is recessed）It is each in face
On individual, to cause that the part span shroud on adjacent blades coordinates and during the rotation of rotor along rubbing each other with matching each other
Ground is wiped to slide.
The content of the invention
One exemplary but non-limiting embodiment in, i.e. the first aspect of the invention, there is provided one kind is used for
The rotatable blades of turbine, the rotatable blades include：Airfoil section, it has leading edge and trailing edge, radially-inwardly holds and footpath
To outward；Root segment, it is connected on the radially-inwardly end of airfoil section；And the substantially part span shroud of tear drop shape, its
Between being positioned on airfoil section in root segment and radially outward holding, wherein the part span shroud has following such cross section
Shape：As measured by the leading edge from the part span shroud, the maximum gauge of the shape of cross section is located at from part span shroud
Leading edge to part span shroud trailing edge extend chord length 20% to 40% within.
As above described in first aspect, wherein the maximum gauge is located at about the 30% of the chord length.
As above described in first aspect, wherein the maximum gauge is located between the 31% and 37% of the chord length.
As above described in first aspect, wherein the maximum gauge is located at the 31% of the chord length, and wherein described part
Span shroud has the profile as defined in X-Y coordinate listed in Table I.
As above described in first aspect, wherein the maximum gauge is located at the 36% of the chord length, and wherein described part
Span shroud has the profile as defined in X-Y coordinate listed in Table II.
As above described in first aspect, wherein the maximum gauge is located at the 37% of the chord length, and wherein described part
Span shroud has the profile as defined in X-Y coordinate listed in Table III.
As above described in first aspect, wherein the part span shroud is generally located at along the radical length of the airfoil section
It is middle.
As above described in first aspect, wherein the rotating vane is run as one of the following：
Preceding grade blade in compressor,
Rear grade blade in combustion gas turbine, or
Low pressure stage blade in steam turbine.
As above described in first aspect, wherein part on the corresponding pressure face and suction surface of the adjacent blades of the blade across
Coordinate at least in part along adjacent, substantially Z-shaped contact surface away from shroud.
As above described in first aspect, wherein part on the corresponding pressure face and suction surface of the adjacent blades of the blade across
There is the contact surface of general straight away from shroud.
In another illustrative aspect, there is provided a kind of turbine, the turbine includes：It is rotatably installed in stator
Rotor, the rotor include axle；At least one rotor wheel mounted on the shaft, each bag at least one rotor wheel
Include the blade that multiple mounted thereto extends radially outwardly；And wherein each blade includes airfoil section, and it has leading edge
With trailing edge, radially-inwardly end and radially outward end, pressure face and suction surface；Root segment, it is located at the airfoil section radially-inwardly
At end；And part span shroud, between it is positioned on airfoil section in root segment and radially outward holds, in pressure face and suction
On face, wherein the part span shroud has the shape of cross section of substantially tear drop shape, such as the leading edge institute from the part span shroud
Measurement, the maximum gauge of the shape of cross section is located at and prolongs between the leading edge of part span shroud and the trailing edge of part span shroud
Within the 20% to 40% of the chord length stretched.
Maximum gauge as described above is located at the 31% of the chord length, and wherein described part span shroud has by Table I
In profile defined in listed X-Y coordinate.
Maximum gauge as described above is located at the 36% of the chord length, and wherein described part span shroud has by table
Profile defined in listed X-Y coordinate in II.
As above maximum gauge described in be located at the chord length 37% at, and wherein described part span shroud have by
Profile defined in listed X-Y coordinate in Table III.
Blade as described above works as one of the following：
Preceding grade blade in compressor,
Rear grade blade in combustion gas turbine, or
Low pressure stage blade in steam turbine.
Part as described above span shroud is generally located at centre along the radical length of the airfoil section.
In another illustrative aspect, a kind of turbine includes：The rotor in stator is rotatably installed in, the rotor bag
Include axle；At least one rotor wheel mounted on the shaft, each at least one rotor wheel is including mounted thereto
The blade that multiple extends radially outwardly；And wherein each blade includes airfoil section, it has leading edge and trailing edge, radially-inwardly
End and radially outward end, pressure face and suction surface；Root segment, it is located at the radially-inwardly end of the airfoil section；And part across
Away from shroud, between in root segment and radially outward being held on its positioning airfoil section, on pressure face and suction surface, wherein the part across
There is the shape of cross section of tear drop shape away from shroud, as measured by the leading edge from the part span shroud, the shape of cross section is most
Big thickness is located at the 31% to 37% of the chord length extended between the leading edge of part span shroud and the trailing edge of part span shroud；
And wherein as measured by the root segment from blade, the part span shroud is placed on airfoil section the radial direction in the airfoil section
Between about the 40% of height and 80%.
Part span shroud as described above has by X-Y coordinate listed in Table I to Table III respectively or by the seat
The defined profile of target geometry scaling.
Part span shroud on the corresponding pressure face and suction surface of the adjacent blades of blade as described above is along adjacent, big
The straight or Z-shaped contact surface of body coordinates at least in part.
Part span shroud as described above is generally located at centre along the radial height of the airfoil section.It is of the invention
These and other aspect, advantage and prominent features will become from detailed description below with reference to accompanying drawing identified below
Obtain obviously.
Brief description of the drawings
Fig. 1 shows the partial cut-away perspective view of conventional steam turbine；
Fig. 2 shows the cross-sectional view of conventional combustion gas turbine；
Fig. 3 shows to incorporate two perspective views of adjacent rotating vane of part span shroud；
Fig. 4 shows two amplifications of a part for adjacent rotating vane including part span shroud obtained from Fig. 3
Perspective view；
Fig. 5 shows to incorporate two top views of a part for adjacent rotating vane of part span shroud, the two phases
Adjacent rotating vane can coordinate along the straight contact surface of adjacent part span shroud section；
Fig. 6 is the schematic cross section of known part span shroud construction；
Fig. 7 is the diagrammatic cross-sectional of of the invention exemplary but non-limiting example part span shroud construction
Face figure；
Fig. 8 is the schematic sectional view similar with Fig. 7, but this illustrate with define part span shroud shape and
Another exemplary embodiment of the X-Y cartesian coordinates of profile；
Fig. 9 is the schematic sectional view similar with Fig. 8, but this illustrate with define part span shroud shape and
Another exemplary embodiment of the X-Y cartesian coordinates of profile；And
Figure 10 is the schematic sectional view similar with Fig. 8 and Fig. 9, but this illustrates to have and defines part span shroud
Another exemplary embodiment of the X-Y cartesian coordinates of shape and profile.
It should be noted that accompanying drawing of the invention is not necessarily to scale.Accompanying drawing is only intended to describe typical pattern of the invention, therefore
It is not construed as limiting the scope of the present invention.
Specific embodiment
As described below, the steam and combustion gas turbine that embodiments of the invention can be applied to used in power generation start
Both machines.It will be appreciated, however, that the teaching is similarly applied to other motors, including（But it is not limited to）Combustion gas turbine starts
Combustion gas turbine used in machine compressor, blower fan and aviation.Those skilled in the art will be further appreciated that the present invention can
It is applied to the machine of above-mentioned different zoom version.
Fig. 1 shows the partial cut-away perspective view of steam turbine 10.Steam turbine 10 includes rotor assembly 12, this turn
Sub-component includes axle or rotor 14 and multiple axially spaced rotor wheels 18.Multiple rotatable blades or movable vane 20 mechanically join
It is connected in each rotor wheel 18.More precisely, blade 20 is arranged to the row extended circumferentially over upon around each rotor wheel 18.It is multiple
Fixed blade 22 is extended circumferentially over upon and is axially positioned between the adjacent row of blade 20 around axle 14.The grade fixed blade 22 is consolidated
Determine to be cooperated onto surrounding stator and with rotatable blades 20 to form one of multiple stage of turbines, and limit through turbine 10
Vapor flow path a part.
In operation, steam 24 is guided into the import 26 of turbine 10 and by fixed blade 22.Wheel blade 22
Steam 24 is abutted against into blade 20 downstream to guide.Steam 24 passes through remaining level, so as to the applying power on blade 20, causes axle
Or rotor 14 rotates.At least one end of turbine 10 can via axle 14 it is axially extending away from rotor 12 and could attach to load or
Other machines（It is not shown）, such as, but not limited to, on generator and/or another turbine.Therefore, big steam turbine unit
Actually may include coaxially to be connected to some turbines on same axle 14.Such a unit can（For example）Including being connected to
Pressure turbine on intermediate pressure turbine machine, the intermediate pressure turbine machine is connected on low-pressure turbine in turn.
Steam turbine 10 shown in Fig. 1 includes five levels.This five levels are referred to as L0, L1, L2, L3 and L4.Level L4
It is the first order and is minimum in this five levels（In radial directions）.Level L3 is the second level and is in the axial direction
Next stage.Level L2 is the third level and the centre being shown as in this five levels.Level L1 is the fourth stage and is penultimate stage.Level
L0 is afterbody and is maximum（In radial directions）.It will be appreciated that there may be more or less than five levels.
Reference picture 2, shows the cross-sectional view of combustion gas turbine 110.Combustion gas turbine 110 includes rotor assembly 112, should
Rotor assembly includes axle 114 and multiple axially spaced rotor wheels 118.In certain embodiments, multiple rotating vanes or dynamic
Leaf 120 is mechanically coupled in each rotor wheel 118.More precisely, blade 120 is arranged to around each rotor wheel 118 weeks
To the row that ground extends.Multiple fixed blades 122 are fixed on surrounding stator and are extended circumferentially over upon around axle 114, axially position
Between the adjacent row of blade 120.
During operation, the air under atmospheric pressure is by compressor compresses and is transported to combustion stage.In the combustion stage
（Represented by combustion chamber 124）In, it is added in the air for leaving compressor and produced air/combustion of burning by by fuel
Expect mixture to heat the air.The air-flow caused due to burning of the fuel in combustion stage is then expanded across turbine
110, so as to convey its portion of energy to drive turbine 110 and produce machine power.In order to produce driving torque, turbine
110 are made up of one or more levels.Every grade of skate leaf 122 and row's rotating vane included in rotor wheel 118
120.The inlet guide of wheel blade spontaneous combustion in 122 future level is on blade 120.This drives the rotation of rotor wheel 118 and therefore drives
The rotation of axle 114 is moved, so as to generate machine power.
Hereinafter describe particularly referring to blade 20, but be similarly applied to blade 120.Fig. 3 and Fig. 4 is turned to, in more detail
Show a pair of blades 20.Each blade or movable vane 20 include airfoil section 32.Root segment 34 is connected to the radial direction of airfoil section 32
On inboard end（Or radially-inwardly hold integral with this）.Blade attachment members 36 are prominent from root segment 34.In certain embodiments,
Blade attachment members 36 can be dovetail, but the shape and construction of other blade attachment members have been in the art our institutes
Know and be also covered by this manual.In airfoil section 32 second, opposite end be radially outer sophisticated 38.Aerofoil profile
Construction is formed as including leading edge 40, trailing edge 42, suction surface 44 and pressure face 46.
Part span shroud 48 is attached at the interlude that airfoil section 32 is between root segment 34 and tip 38.Show at this
In example property embodiment, part span shroud section 50,52 is respectively positioned on the suction surface 44 and pressure face 46 of airfoil section 32.
In exemplary embodiment shown in Fig. 3, the part span shroud section 50,52 of adjacent blades 20 is designed to the operation phase in turbine
Between, the Z-shaped edge 54,56 along matching coordinates at least in part（Referring to Fig. 4）, as known part span construction in.
The grade part span shroud section is joined on airfoil section at chamfering 58（For shown in part span shroud section 52, but also use
In part span shroud section 50）.
When part span shroud is when contacting with each other the anti-twisted period of blade, blade stiffness and damping characteristic are improved.
The plurality of blade 20 therefore behaves as the structure of single, continuous connection, the structure when compared with design that is discrete and not coupling,
Show the hardness and damping characteristic of improvement.Blade 20 also shows the vibration stress of reduction.
Fig. 5 shows another known construction, wherein the part span shroud section on adjacent, correspondence blade 64,66
60th, 62 it is designed to coordinate along straight, substantially parallel edge 68,70.
Fig. 6 is shown for part span shroud（On both pressure face and suction surface in aerofoil profile）Known cross section shape
Shape, such as in United States Patent (USP) 5, it is shown and described in 695,323 and be generally used for the shroud as shown in Fig. 3 to Fig. 5 construction.
Note that the maximum gauge of part span cross section is located at, prolong along between the leading edge 74 and trailing edge 76 of part span shroud 78
The length about middle of the string 72 stretched.
Fig. 7 shows of the invention exemplary but non-limiting example the tear for part span shroud 80
Shape shape of cross section.In this manual, the maximum gauge of shape of cross section has moved forward, before the closer part span shroud
Edge 82.More precisely, as measured by from leading edge 82, the point of maximum gauge is located at leading edge 82 respectively in part span shroud 80
In the range of the 20% to 40% of the length of the string 84 extended between trailing edge 86, and preferably at about 30%.Therefore, the part
The thickness of span shroud changes in the opposite direction since the position of maximum gauge.
The part span shroud of above-mentioned tear drop shape is generally located at centre along the radical length of aerofoil profile, but such as from the root segment of blade
It is measured, can be located at the airfoil section radial height about 40% and 80% between any position.
In more specifically exemplary embodiment, as measured by from leading edge 82, the maximum gauge of part span shroud is located at
At the 31% of the length of string 84, as shown in Figure 8.The shape or profile of section are defined by X-Y cartesian coordinates, wherein in X-direction
On zero reference point in the center of string size along its length, and zero reference point in the Y direction is on string 84.Table below
The coordinate in each point shown on sectional view is found in I.The coordinate position in Y=0 in the leading edge of aerofoil profile of reference point 1, and
Points are sequentially advanced in the counterclockwise direction.
Table I
In another exemplary embodiment, as measured by from leading edge 82, maximum gauge is located at the 36% of the length of string 84
Place, as shown in Figure 9.The shape and profile of section are defined by X-Y cartesian coordinates listed in the scheme similar with Fig. 8,
And the coordinate of each point shown on sectional view is found in Table II below.
Table II
In another exemplary embodiment, as measured by from leading edge 82, maximum gauge is located at the 37% of the length of string 84
Place, as shown in Figure 10.The shape and profile of section are come by X-Y cartesian coordinates listed in the scheme similar with Fig. 8 and Fig. 9
Definition, and the coordinate of each point shown on sectional view is found in Table III below.
Table III
It will be appreciated that present invention also contemplates that being scaled with the geometry of the part span shroud profile defined in upper table.
It should also be clear that for the aerofoil profile of development length, part span shroud described in this specification can be located at
Conventional airfoil tip shroud at radially outer sophisticated the 38 of aerofoil profile（Fig. 3, Fig. 4）It is applied in combination.
Above-mentioned blade 20 and part span shroud 80 can be used in various turbine environment.For example, with reference to described in Fig. 7
Blade with part span shroud 80 can work in any one or more following：The prime of compressor；Combustion gas turbine
Rear class；Or the low pressure stage blade in steam turbine.In Fig. 3 to Fig. 5 being can be applied to the shroud of 80 shape of cross sections for representing
Shown part span shroud construction, but it is not limited to those constructions.
Although present specification describes various embodiments, those skilled in the art is from specification it will be appreciated that can
Various combinations, modification are carried out to each key element wherein or is improved, and they are belonged in the scope of the present invention.Additionally, not taking off
In the case of essential scope of the invention, various modifications can be carried out, so that particular case or material adapt to of the invention
Teaching.Therefore, it is intended that the invention is not restricted to implement the particular embodiment of the present invention as optimal mode, conversely, present invention bag
Include all embodiments in scope.
Claims (20)
1. a kind of rotatable blades for turbine, the rotatable blades include：
Airfoil section, it has leading edge and trailing edge, radially-inwardly holds and radially outward hold；
Root segment, it is connected on the radially-inwardly end of the airfoil section；And
The substantially part span shroud of tear drop shape, its be positioned on the airfoil section and the root segment with it is described radially outward
Between end, wherein the part span shroud has following such shape of cross section：Such as from before the part span shroud
Measured by edge, the maximum gauge of the shape of cross section be located at from the leading edge of the part span shroud to the part across
Within the 20% to 40% of the chord length that trailing edge away from shroud extends, the cross-sectional profiles of the tear-shaped portion span shroud are by table
X-Y cartesian coordinates listed by any one in I, Table II, Table III are defined.
2. rotatable blades as claimed in claim 1, wherein the maximum gauge is located at the 30% of the chord length.
3. rotatable blades as claimed in claim 1, wherein the maximum gauge be located at the chord length 31% and 37% it
Between.
4. rotatable blades as claimed in claim 1, wherein the maximum gauge is located at the 31% of the chord length, and its
Described in part span shroud there are the cross-sectional profiles as defined in X-Y coordinate listed in the Table I.
5. rotatable blades as claimed in claim 1, wherein the maximum gauge is located at the 36% of the chord length, and its
Described in part span shroud there are the cross-sectional profiles as defined in X-Y coordinate listed in the Table II.
6. rotatable blades as claimed in claim 1, wherein the maximum gauge is located at the 37% of the chord length, and its
Described in part span shroud there are the cross-sectional profiles as defined in X-Y coordinate listed in the Table III.
7. rotatable blades as claimed in claim 1, wherein the part span shroud is long along the radial direction of the airfoil section
Degree is generally located at centre.
8. rotatable blades as claimed in claim 1, wherein the rotating vane is run as one of the following：
Preceding grade blade in compressor,
Rear grade blade in combustion gas turbine, or
Low pressure stage blade in steam turbine.
9. rotatable blades as claimed in claim 1, wherein the corresponding pressure face of the adjacent blades of the blade and suction surface
On part span shroud coordinate at least in part along adjacent, substantially Z-shaped contact surface.
10. rotatable blades as claimed in claim 1, wherein the corresponding pressure face of the adjacent blades of the blade and suction surface
On part span shroud there is the contact surface of general straight.
A kind of 11. turbines, it includes：
The rotor in stator is rotatably installed in, the rotor includes：
Axle；
At least one rotor wheel on the shaft is installed, each at least one rotor wheel includes mounted thereto
The blade that extends radially outwardly of multiple；And
The blade for wherein being extended radially outwardly described in each includes：Airfoil section, its have leading edge and trailing edge, radially-inwardly end and
Radially outward end, pressure face and suction surface；Root segment, it is located at the radially-inwardly end of the airfoil section；And part
Span shroud, its be positioned on the airfoil section the root segment and it is described radially outward hold between, in the pressure face and
On the suction surface, wherein the part span shroud has the shape of cross section of substantially tear drop shape, such as from the part span
Measured by the leading edge of shroud, the maximum gauge of the shape of cross section is located at the leading edge and institute in the part span shroud
Within stating the 20% to 40% of the chord length extended between the trailing edge of part span shroud, the maximum of the part span shroud
Thickness is 0.275 or 0.36 with the ratio of the chord length.
12. turbines as claimed in claim 11, wherein the maximum gauge is located at the 31% of the chord length, and wherein
The part span shroud has the cross-sectional profiles as defined in X-Y coordinate listed in Table I.
13. turbines as claimed in claim 11, wherein the maximum gauge is located at the 36% of the chord length, and wherein
The part span shroud has the cross-sectional profiles as defined in X-Y coordinate listed in Table II.
14. turbines as claimed in claim 11, wherein the maximum gauge is located at the 37% of the chord length, and wherein
The part span shroud has the cross-sectional profiles as defined in X-Y coordinate listed in Table III.
15. turbines as claimed in claim 11, wherein the blade works as one of the following：
Preceding grade blade in compressor,
Rear grade blade in combustion gas turbine, or
Low pressure stage blade in steam turbine.
16. turbines as claimed in claim 11, wherein radical length of the part span shroud along the airfoil section
It is generally located at centre.
A kind of 17. turbines, it includes：
The rotor in stator is rotatably installed in, the rotor includes：
Axle；
At least one rotor wheel on the shaft is installed, each at least one rotor wheel includes mounted thereto
The blade that extends radially outwardly of multiple；And
Wherein each blade includes：Airfoil section, it has leading edge and trailing edge, radially-inwardly end and radially outward end, pressure face
And suction surface；Root segment, it is located at the radially-inwardly end of the airfoil section；And part span shroud, it is positioned at
On the airfoil section between the root segment and the radially outward end, on the pressure face and the suction surface, wherein
The part span shroud has the shape of cross section of substantially tear drop shape, as measured by the leading edge from the part span shroud,
The maximum gauge of the shape of cross section is located at the leading edge and the part span shroud in the part span shroud
At 31%, 36% or the 37% of the chord length extended between trailing edge；And wherein as measured by the root segment from the blade, institute
Part span shroud is stated to be placed on the airfoil section between about the 40% to 80% of the radial height of the airfoil section,
The maximum gauge of the part span shroud is 0.275 or 0.360 with the ratio of the chord length.
18. turbines as claimed in claim 17, wherein the part span shroud has by respectively in Table I, Table II and table
X-Y coordinate listed by any one in III or the defined cross-sectional profiles of geometry scaling by the coordinate.
19. turbines as claimed in claim 17, wherein on the corresponding pressure face and suction surface of the adjacent blades of the blade
Part span shroud coordinate at least in part along adjacent, general straight or Z-shaped contact surface.
20. turbines as claimed in claim 17, wherein the radial direction of the part span shroud along the airfoil section
Highly it is generally located at centre.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/691,478 | 2012-11-30 | ||
| US13/691,478 US20140154081A1 (en) | 2012-11-30 | 2012-11-30 | Tear-drop shaped part-span shroud |
| US13/691478 | 2012-11-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103850716A CN103850716A (en) | 2014-06-11 |
| CN103850716B true CN103850716B (en) | 2017-06-20 |
Family
ID=49596117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310627609.7A Active CN103850716B (en) | 2012-11-30 | 2013-11-29 | The part span shroud of tear drop shape |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140154081A1 (en) |
| EP (1) | EP2738351A1 (en) |
| JP (1) | JP2014109272A (en) |
| CN (1) | CN103850716B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104763477B (en) * | 2015-04-13 | 2016-03-02 | 大连理工大学 | A kind of turbomachine movable vane tip segment shroud structure |
| EP3379033A1 (en) * | 2017-03-20 | 2018-09-26 | General Electric Company | Systems and methods for minimizing an incidence angle between a number of streamlines in a not disturbed flow field by varying an inclination angle of a chord line of a snubber |
| US11339670B2 (en) | 2020-10-13 | 2022-05-24 | General Electric Company | Part-span shroud configurations |
| JP7245215B2 (en) * | 2020-11-25 | 2023-03-23 | 三菱重工業株式会社 | steam turbine rotor blade |
| EP4112884A1 (en) * | 2021-07-01 | 2023-01-04 | Doosan Enerbility Co., Ltd. | Blade for a turbomachine, blade assembly, and turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5257908A (en) * | 1991-11-15 | 1993-11-02 | Ortolano Ralph J | Turbine lashing structure |
| US5695323A (en) * | 1996-04-19 | 1997-12-09 | Westinghouse Electric Corporation | Aerodynamically optimized mid-span snubber for combustion turbine blade |
| CN101333936A (en) * | 2007-06-27 | 2008-12-31 | 株式会社东芝 | Steam turbine, and intermediate support structure for holding row of long moving blades therein |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1618284A (en) * | 1925-05-22 | 1927-02-22 | Westinghouse Electric & Mfg Co | Turbine-blade bracing |
| US1747690A (en) * | 1927-12-15 | 1930-02-18 | Westinghouse Electric & Mfg Co | Blade lashing |
| US2117107A (en) * | 1935-09-28 | 1938-05-10 | Westinghouse Electric & Mfg Co | Turbine blade lashing |
| JPS60111001A (en) * | 1983-11-21 | 1985-06-17 | Mitsubishi Heavy Ind Ltd | Integral stub blade for turbine |
| JP2007187053A (en) * | 2006-01-12 | 2007-07-26 | Hitachi Ltd | Turbine blade |
| JP4713509B2 (en) * | 2007-01-26 | 2011-06-29 | 株式会社日立製作所 | Turbine blade |
| US8075272B2 (en) * | 2008-10-14 | 2011-12-13 | General Electric Company | Steam turbine rotating blade for a low pressure section of a steam turbine engine |
| JP5558095B2 (en) * | 2009-12-28 | 2014-07-23 | 株式会社東芝 | Turbine blade cascade and steam turbine |
-
2012
- 2012-11-30 US US13/691,478 patent/US20140154081A1/en not_active Abandoned
-
2013
- 2013-11-15 EP EP13193148.7A patent/EP2738351A1/en not_active Ceased
- 2013-11-26 JP JP2013243435A patent/JP2014109272A/en active Pending
- 2013-11-29 CN CN201310627609.7A patent/CN103850716B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5257908A (en) * | 1991-11-15 | 1993-11-02 | Ortolano Ralph J | Turbine lashing structure |
| US5695323A (en) * | 1996-04-19 | 1997-12-09 | Westinghouse Electric Corporation | Aerodynamically optimized mid-span snubber for combustion turbine blade |
| CN101333936A (en) * | 2007-06-27 | 2008-12-31 | 株式会社东芝 | Steam turbine, and intermediate support structure for holding row of long moving blades therein |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2738351A1 (en) | 2014-06-04 |
| CN103850716A (en) | 2014-06-11 |
| US20140154081A1 (en) | 2014-06-05 |
| JP2014109272A (en) | 2014-06-12 |
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